Patents Examined by Philip J Bonzell
  • Patent number: 11312490
    Abstract: An example UAV landing structure includes a landing platform for a UAV, a cavity within the landing platform, and a track that runs along the landing platform and at least a part of the cavity. The UAV may include a winch system that includes a tether that may be coupled to a payload. Furthermore, the cavity may be aligned over a predetermined target location. The cavity may be sized to allow the winch system to pass a tethered payload through the cavity. The track may guide the UAV to a docked position over the cavity as the UAV moves along the landing platform. When the UAV is in the docked position, a payload may be loaded to or unloaded from the UAV through the cavity.
    Type: Grant
    Filed: March 12, 2020
    Date of Patent: April 26, 2022
    Assignee: WING AVIATION LLC
    Inventors: Jesse Blake, Jim Schmalzried, Trevor Shannon, Michael Simonian, Sindre Klepp, Stephen Benson, Adam Woodworth
  • Patent number: 11312466
    Abstract: A system for deploying an inflatable structure may include a balloon defining an envelope having a first stiffness, a valve assembly including a control valve, and a reactor defining a chamber having a second stiffness, the valve assembly disposed in fluid communication between the chamber and the envelope, the control valve selectively actuatable to control fluid communication between the chamber and the envelope, the second stiffness of the chamber greater than the first stiffness of the envelope, and the reactor foldable onto itself along the chamber and elastically deformable to unfold in response to an increase in pressure in the chamber.
    Type: Grant
    Filed: September 14, 2021
    Date of Patent: April 26, 2022
    Assignee: LTAG SYSTEMS LLC
    Inventors: Jonathan T. Slocum, Alexander H. Slocum
  • Patent number: 11305875
    Abstract: A method for operating a vehicle chassis includes providing the vehicle chassis including a main body and at least one compartment arranged on the vehicle chassis, selectively receiving one or more components in the compartment, and effecting an operational state of a vehicle comprising the vehicle chassis based on a type of at least one of the one or more components that are selectively received in the compartment. The one or more components is selected from a plurality of components of different types.
    Type: Grant
    Filed: January 11, 2019
    Date of Patent: April 19, 2022
    Assignee: SZ DJI TECHNOLOGY CO., LTD.
    Inventors: Hanping Chen, Xiangyu Chen, Mingxi Wang, Qi Zhou
  • Patent number: 11299252
    Abstract: A rectification structure body 100 of a flying vehicle is provided with a rectification section 30, a heat input control section 20 and a vacuum thermal insulation section 10. The rectification section 30 has a rectification surface 30a and a back surface 30b. The rectification surface 30a rectifies airflow 5 from a travelling direction. The back surface 30b is arranged opposite to the rectification surface 30a. The heat input control section 20 is connected to the back surface 30b. The vacuum thermal insulation section 10 is connected to the heat input control section 20 and its surface is formed of rigid body. In addition, the heat input control section 20 is sandwiched between the back surface 30b and the vacuum thermal insulation section 10.
    Type: Grant
    Filed: September 12, 2018
    Date of Patent: April 12, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Rikako Yoshida, Kosuke Nishikawa
  • Patent number: 11299266
    Abstract: A wing for an aircraft includes, but is not limited to, a wing body having a wingtip, a leading-edge, and a trailing edge. The wingtip comprises an outboard-most portion of the wing body. The leading-edge is disposed along a forward portion of the wing body and is configured to cause a vortex to extend off the trailing edge at a location inboard of the wingtip when the aircraft is flown sub-sonically at a predetermined angle of attack. The trailing edge is disposed along an aft portion of the wing body and has an aft-most region disposed inboard of the wingtip at a position that corresponds with the location where the vortex extends off the trailing edge.
    Type: Grant
    Filed: October 25, 2017
    Date of Patent: April 12, 2022
    Assignee: Gulfstream Aerospace Corporation
    Inventors: George Hicks, Donald Howe, Gregory Howe, Joe Gavin
  • Patent number: 11300199
    Abstract: A non-pressurized accessory gearbox for an aircraft includes: a housing, one or more gears disposed within the housing, an input rotating member to receive input from a main rotor gearbox via a shaft connected to the one or more gears, and one or more output rotating members in communication with the one or more gears. The gearbox is configured to utilize splash lubrication for moving a lubrication fluid within the housing.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: April 12, 2022
    Assignee: TEXTRON INNOVATIONS INC.
    Inventors: Scott David Poster, Walter Riley, Gary Cope, Charles Hubert Speller, Jr.
  • Patent number: 11292583
    Abstract: Systems, devices, and methods including an unmanned aerial vehicle (UAV); one or more inner wing panels of the UAV; one or more outer wing panels of the UAV; at least one inboard propeller attached to at least one engine disposed on the one or more inner wing panels; at least one tip propeller attached to at least one engine disposed on the one or more outer wing panels; at least one microcontroller configured to: determine an angular position of the at least one inboard propeller; and send a signal to halt rotation of the at least one inboard propeller such that the at least one inboard propeller is held in an attitude that provides for clearance of the propeller blade to the ground upon landing.
    Type: Grant
    Filed: December 7, 2020
    Date of Patent: April 5, 2022
    Assignee: AEROVIRONMENT, INC.
    Inventor: Bart Dean Hibbs
  • Patent number: 11292571
    Abstract: A door arrangement for an aircraft segment, which door arrangement comprises a passenger door, a fuselage portion accommodating the passenger door, and a girt bar for arming and disarming an emergency slide. The passenger door is movable relative to the fuselage portion between a raised position and a lowered position. The girt bar is connectable by means of a connecting arrangement to the passenger door and/or to the fuselage portion. The connecting arrangement comprises a mechanism which is configured to, during arming of the emergency slide, actuate a locking mechanism of an engagement device fastened to the fuselage portion, in such a way that the girt bar is fixed in a decouplable manner to the engagement device.
    Type: Grant
    Filed: January 28, 2020
    Date of Patent: April 5, 2022
    Assignee: Airbus Operations GmbH
    Inventor: Luc Andreani
  • Patent number: 11293463
    Abstract: A cowl door actuator is arranged between a head end and a rod end connected to a cowl door in an aircraft. The cowl door has a closed position and an open position, and the cowl door actuator includes a piston rod that is axially moveable between the head end and the rod end. The piston rod has an extended position in which the piston rod contacts the rod end to move the cowl door to the open position, and a retracted position in which the piston rod is axially spaced from the rod end. When the cowl door is in the closed position, the gap between the piston rod and the rod end enables an axial displacement of the piston rod toward the extended position during thermal expansion of fluid remaining in the actuator, such that the cowl door is maintained in the closed position.
    Type: Grant
    Filed: July 23, 2019
    Date of Patent: April 5, 2022
    Assignee: Parker-Hannifin Corporation
    Inventor: David J. Bouman
  • Patent number: 11286054
    Abstract: A propulsion system for an aircraft is disclosed, and includes a first propeller, a second propeller, a first hybrid propulsion system, a second hybrid propulsion system, and a cross-connecting clutch. The first hybrid propulsion system includes a first motor coupled to a first engine by a first overrunning clutch, where the first hybrid propulsion system is operably coupled to drive the first propeller. The second hybrid propulsion system includes a second motor coupled to a second engine by a second overrunning clutch, where the second hybrid propulsion system is operably coupled to drive the second propeller. The cross-connecting clutch is operably coupled to both the first hybrid propulsion system and the second hybrid propulsion system and configured to actuate into an engaged position.
    Type: Grant
    Filed: October 2, 2019
    Date of Patent: March 29, 2022
    Assignee: The Boeing Company
    Inventor: Michael Thomas Fox
  • Patent number: 11286037
    Abstract: A rotor system is provided in one example embodiment and may include a rotor duct; at least one rotor blade, wherein the at least one rotor blade comprises a tip end; and a tip extension affixed at the tip end of the at least one rotor blade, wherein the tip extension comprises a plurality of flexible elements and the rotor blade has a fixed extended length based on the tip extension. The tip extension may provide a clearance distance between the tip extension and the rotor duct.
    Type: Grant
    Filed: October 12, 2018
    Date of Patent: March 29, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Robert Glenn Vaughn, Michael J. Ryan, Brent Randal Achttien, Kirk L. Groninga, Daniel B. Robertson, Matthew Edward Louis
  • Patent number: 11286035
    Abstract: A propulsion device with double-layer flow guiding assembly and a flight vehicle using the same are provided. The propulsion device includes a propulsion body, a first-layer flow guiding assembly and a second-layer flow guiding assembly. The propulsion body includes a housing, an airflow suction port and an airflow discharge port. The first-layer flow guiding assembly includes a front flow guiding ring and at least one first-layer flow guiding plate. The front flow guiding ring is disposed outside the airflow discharge port and has a first axis. The front flow guiding ring swings relative to the airflow discharge port along a first rotation axis. The first rotation axis intersects the first axis. The first-layer flow guiding plate is fixed in the front flow guiding ring and extends along the first rotation axis. The second-layer flow guiding assembly has a structure similar to the first-layer flow guiding assembly.
    Type: Grant
    Filed: July 9, 2020
    Date of Patent: March 29, 2022
    Inventor: Yao-Chang Lin
  • Patent number: 11286067
    Abstract: A system includes a first component, a second component, a locking pin, and an interface assembly that is configured to selectively adjust a stiffness of a coupling interface between the first component and the second component. The interface assembly includes at least one support coupler secured to the first component. The support coupler(s) includes a main body, a first arm extending from a first side of the main body, a second arm extending from a second side of the main body, and a flange extending from the main body. The flange includes a locking pin hole that is configured to selectively receive the locking pin. The locking pin is selectively moveable between a retracted position in which the locking pin is out of the locking pin hole, and a deployed position in which the locking pin extends into the locking pin hole and a portion of the first component and locks the interface assembly to the first component.
    Type: Grant
    Filed: October 9, 2018
    Date of Patent: March 29, 2022
    Assignee: THE BOEING COMPANY
    Inventors: Jeffrey W. Weathers, Dustin Gregory Padgett
  • Patent number: 11286036
    Abstract: A rotor system is provided in one example embodiment and may include a rotor duct; at least one rotor blade, wherein the at least one rotor blade comprises a tip end; and a tip extension affixed at the tip end of the at least one rotor blade, wherein the tip extension is comprised, at least in part, of a flexible material and the rotor blade has a fixed extended length based on the tip extension. The tip extension may provide a clearance distance between the tip extension and the rotor duct.
    Type: Grant
    Filed: October 12, 2018
    Date of Patent: March 29, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Kirk L. Groninga, Daniel B. Robertson, Matthew Edward Louis, Robert Glenn Vaughn, Michael J. Ryan, Brent Randal Achttien
  • Patent number: 11286062
    Abstract: A spacecraft includes a structural interface adapter for mating to a launch vehicle, at least one radiator panel, at least one equipment panel, a first 3-D truss structure proximal to and mechanically coupled with the structural interface adapter, and a second 3-D truss structure distal from the structural interface adapter and coupled mechanically with the structural interface adapter by way of the first 3-D truss structure. The at least one equipment panel and the at least one exterior radiator panel is coupled mechanically by one or both of the first 3-D truss structure and the second 3-D truss structure with the structural interface adapter. Each 3-D truss structure includes at least four coupling nodes and at least six strut elements, attached together by a respective plurality of joints, each strut element disposed between and attached with a respective pair of the plurality of coupling nodes.
    Type: Grant
    Filed: August 13, 2019
    Date of Patent: March 29, 2022
    Assignee: Space Systems/Loral, LLC
    Inventor: Michael Paul Freestone
  • Patent number: 11279498
    Abstract: A support member configured to support a first structure within an aperture of a second structure is disclosed. The support member comprises a bracket for attaching the support member to the second structure; and a funnel part. The diameter of the base of the funnel is less than or equal to the diameter of the aperture, and is substantially equal to the diameter of a part of the first structure to be supported by the support member.
    Type: Grant
    Filed: July 24, 2019
    Date of Patent: March 22, 2022
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: David Petit, Eric Bonte, Daniel Peachey
  • Patent number: 11279468
    Abstract: An aircraft surface cover is provided. The aircraft surface cover includes a cover member that is configured to be removably secured to an aircraft structure. The cover member includes an exterior surface that has a microtextured surface including microtexture ribs that are configured to improve aerodynamic performance of the aircraft structure.
    Type: Grant
    Filed: January 22, 2019
    Date of Patent: March 22, 2022
    Assignee: THE BOEING COMPANY
    Inventors: Michelle Crivella, Matthew Berden
  • Patent number: 11279476
    Abstract: A passive hub flapping lock including: one or more lever arms, each lever arm rotatably coupled to a pivot and comprising a first lever arm end and a second lever arm end; one or more stop wedges; one or more frames coupled to the one or more stop wedges, each frame coupled to the first lever arm end of one of the one or more lever arms; one or more weight sets, each weight set comprising one or more weights coupled to the second lever arm end of one of the one or more lever arms; and one or more pivot torsion springs, each pivot torsion spring positioned at the pivot.
    Type: Grant
    Filed: November 24, 2020
    Date of Patent: March 22, 2022
    Assignee: TEXTRON INNOVATIONS INC.
    Inventor: Kyle Thomas Cravener
  • Patent number: 11273898
    Abstract: A cargo compartment module for an aircraft, including at least one floor, at least one side wall that is connected to the floor, upper installation points for connecting the side wall to the main deck, in particular transverse supports of the main deck, lower installation points for connecting the side wall to frames and/or other structural elements of the aircraft, wherein the side wall has reinforcements such that the side wall in an installed state forms part of the load-bearing structure of the aircraft and/or supports the main deck.
    Type: Grant
    Filed: November 24, 2020
    Date of Patent: March 15, 2022
    Assignee: TELAIR INTERNATIONAL GMBH
    Inventor: Thomas Huber
  • Patent number: 11273900
    Abstract: A thermal management system for transferring heat from a heat load includes a composite structural member that supports a heat load source and a heat transfer member in thermal contact with the composite structural member, and in thermal contact with a heat sink. The system further includes at least one thermally-conductive first fastener that is in thermal contact with the heat transfer member, couples the heat load source to the composite structural member, and conducts heat from the heat load source into the heat transfer member. The heat transfer member conducts heat from the thermally-conductive first fastener to the heat sink.
    Type: Grant
    Filed: June 18, 2020
    Date of Patent: March 15, 2022
    Assignee: THE BOEING COMPANY
    Inventor: Edward V. White